Leading-edge bluntness effects on hypersonic three-dimensional flows over a compression ramp

Uterine fibroid tissues are often compared to their matched myometrium in an effort to understand their pathophysiology, but it is not clear whether the myometria of uterine fibroid patients represent truly non-disease control tissues. We analyzed the transcriptomes of myometrial samples from non-fibroid patients (M) and compared them with fibroid (F) and matched myometrial (MF) samples to determine whether there is a phenotypic difference between fibroid and non-fibroid myometria. Multidimensional scaling plots revealed that M samples clustered separately from both MF and F samples. A total of 1169 differentially expressed genes (DEGs) (false discovery rate < 0.05) were observed in the MF comparison with M. Overrepresented Gene Ontology terms showed a high concordance of upregulated gene sets in MF compared to M, particularly extracellular matrix and structure organization. Gene set enrichment analyses showed that the leading-edge genes from the TGFβ signaling and inflammatory response gene sets were significantly enriched in MF. Overall comparison of the three tissues by three-dimensional principal component analyses showed that M, MF, and F samples clustered separately from each other and that a total of 732 DEGs from F vs. M were not found in the F vs. MF, which are likely understudied in the pathogenesis of uterine fibroids and could be key genes for future investigation. These results suggest that the transcriptome of fibroid-associated myometrium is different from that of non-diseased myometrium and that fibroid studies should consider using both matched myometrium and non-diseased myometrium as controls.

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Three-Dimensional and Rotational Aerodynamics on the NREL Phase VI Wind Turbine Blade

Journal of Solar Energy Engineering ◽

10.1115/1.2931506 ◽

2008 ◽

Vol 130 (3) ◽

Cited By ~ 10

Author(s):

Alvaro Gonzalez ◽

Xabier Munduate

Keyword(s):

Wind Turbine ◽

Turbine Blade ◽

Three Dimensional ◽

Separated Flow ◽

Leading Edge ◽

Wind Turbine Blade ◽

Trailing Edge ◽

Rotating Blade ◽

Nrel Phase Vi ◽

Edge Separation

This work undertakes an aerodynamic analysis over the parked and the rotating NREL Phase VI wind turbine blade. The experimental sequences from NASA Ames wind tunnel selected for this study respond to the parked blade and the rotating configuration, both for the upwind, two-bladed wind turbine operating at nonyawed conditions. The objective is to bring some light into the nature of the flow field and especially the type of stall behavior observed when 2D aerofoil steady measurements are compared to the parked blade and the latter to the rotating one. From averaged pressure coefficients together with their standard deviation values, trailing and leading edge separated flow regions have been found, with the limitations of the repeatability of the flow encountered on the blade. Results for the parked blade show the progressive delay from tip to root of the trailing edge separation process, with respect to the 2D profile, and also reveal a local region of leading edge separated flow or bubble at the inner, 30% and 47% of the blade. For the rotating blade, results at inboard 30% and 47% stations show a dramatic suppression of the trailing edge separation, and the development of a leading edge separation structure connected with the extra lift.

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Experimental Studies of Leading Edge Contouring Influence on Secondary Losses in Transonic Turbines

Volume 8: Turbomachinery, Parts A, B, and C ◽

10.1115/gt2012-68497 ◽

2012 ◽

Cited By ~ 1

Author(s):

Ranjan Saha ◽

Jens Fridh ◽

Torsten Fransson ◽

Boris I. Mamaev ◽

Mats Annerfeldt

Keyword(s):

Gas Turbine ◽

Guide Vane ◽

Experimental Studies ◽

Three Dimensional ◽

Leading Edge ◽

Secondary Flows ◽

Noticeable Effect ◽

Flow Angle ◽

Wide Range ◽

Contour Plots

An experimental study of the hub leading edge contouring using fillets is performed in an annular sector cascade to observe the influence of secondary flows and aerodynamic losses. The investigated vane is a three dimensional gas turbine guide vane (geometrically similar) with a mid-span aspect ratio of 0.46. The measurements are carried out on the leading edge fillet and baseline cases using pneumatic probes. Significant precautions have been taken to increase the accuracy of the measurements. The investigations are performed for a wide range of operating exit Mach numbers from 0.5 to 0.9 at a design inlet flow angle of 90°. Data presented include the loading, fields of total pressures, exit flow angles, radial flow angles, as well as profile and secondary losses. The vane has a small profile loss of approximately 2.5% and secondary loss of about 1.1%. Contour plots of vorticity distributions and velocity vectors indicate there is a small influence of the vortex-structure in endwall regions when the leading edge fillet is used. Compared to the baseline case the loss for the filleted case is lower up to 13% of span and higher from 13% to 20% of the span for a reference condition with Mach no. of 0.9. For the filleted case, there is a small increase of turning up to 15% of the span and then a small decrease up to 35% of the span. Hence, there are no significant influences on the losses and turning for the filleted case. Results lead to the conclusion that one cannot expect a noticeable effect of leading edge contouring on the aerodynamic efficiency for the investigated 1st stage vane of a modern gas turbine.

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Aerodynamic Measurements on the Interaction of Secondary Jets and Separation Bubble

ASME 2012 Gas Turbine India Conference ◽

10.1115/gtindia2012-9537 ◽

2012 ◽

Author(s):

A. Samson ◽

S. Sarkar

Keyword(s):

Flat Plate ◽

Large Scale ◽

Separation Bubble ◽

Three Dimensional ◽

Leading Edge ◽

Bubble Interactions ◽

Separated Shear Layer ◽

Bubble Length ◽

Flow Visualizations ◽

Turbulence Generation

The dynamics of separation bubble under the influence of continuous jets ejected near the semi-circular leading edge of a flat plate is presented. Two different streamwise injection angles 30° and 60° and velocity ratios 0.5 and 1 for Re = 25000 and 55000 (based on the leading-edge diameter) are considered here. The flow visualizations illustrating jet and separated layer interactions have been carried out with PIV. The objective of this study is to understand the mutual interactions of separation bubble and the injected jets. It is observed that flow separates at the blending point of semi-circular arc and flat plate. The separated shear layer is laminar up to 20% of separation length after which perturbations are amplified and grows in the second-half of the bubble leading to breakdown and reattachment. Blowing has significantly affected the bubble length and thus, turbulence generation. Instantaneous flow visualizations supports the unsteadiness and development of three-dimensional motions leading to formation of Kelvin-Helmholtz rolls and shedding of large-scale vortices due to jet and bubble interactions. In turn, it has been seen that both the spanwise and streamwise dilution of injected air is highly influenced by the separation bubble.

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Pericyte contractility controls endothelial cell cycle progression and sprouting: insights into angiogenic switch mechanics

AJP Cell Physiology ◽

10.1152/ajpcell.00185.2014 ◽

2014 ◽

Vol 307 (9) ◽

pp. C878-C892 ◽

Cited By ~ 21

Author(s):

Jennifer T. Durham ◽

Howard K. Surks ◽

Brian M. Dulmovits ◽

Ira M. Herman

Keyword(s):

Cell Cycle Progression ◽

Network Formation ◽

Rho Gtpase ◽

Three Dimensional ◽

Rho Kinase ◽

Leading Edge ◽

Fold Increase ◽

Cycle Progression ◽

Interacting Protein ◽

Angiogenic Switch

Microvascular stability and regulation of capillary tonus are regulated by pericytes and their interactions with endothelial cells (EC). While the RhoA/Rho kinase (ROCK) pathway has been implicated in modulation of pericyte contractility, in part via regulation of the myosin light chain phosphatase (MLCP), the mechanisms linking Rho GTPase activity with actomyosin-based contraction and the cytoskeleton are equivocal. Recently, the myosin phosphatase-RhoA-interacting protein (MRIP) was shown to mediate the RhoA/ROCK-directed MLCP inactivation in vascular smooth muscle. Here we report that MRIP directly interacts with the β-actin-specific capping protein βcap73. Furthermore, manipulation of MRIP expression influences pericyte contractility, with MRIP silencing inducing cytoskeletal remodeling and cellular hypertrophy. MRIP knockdown induces a repositioning of βcap73 from the leading edge to stress fibers; thus MRIP-silenced pericytes increase F-actin-driven cell spreading twofold. These hypertrophied and cytoskeleton-enriched pericytes demonstrate a 2.2-fold increase in contractility upon MRIP knockdown when cells are plated on a deformable substrate. In turn, silencing pericyte MRIP significantly affects EC cycle progression and angiogenic activation. When MRIP-silenced pericytes are cocultured with capillary EC, there is a 2.0-fold increase in EC cycle entry. Furthermore, in three-dimensional models of injury and repair, silencing pericyte MRIP results in a 1.6-fold elevation of total tube area due to EC network formation and increased angiogenic sprouting. The pivotal role of MRIP expression in governing pericyte contractile phenotype and endothelial growth should lend important new insights into how chemomechanical signaling pathways control the “angiogenic switch” and pathological angiogenic induction.

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Base-Vented Hydrofoils of Finite Span Under a Free Surface: An Experimental Investigation

Journal of Ship Research ◽

10.5957/jsr.1984.28.2.90 ◽

1984 ◽

Vol 28 (02) ◽

pp. 90-106

Author(s):

Jacques Verron ◽

Jean-Marie Michel

Keyword(s):

Experimental Investigation ◽

Free Surface ◽

Flow Rate ◽

Cavity Length ◽

Three Dimensional ◽

Leading Edge ◽

Pulsation Frequency ◽

Cavity Pressure ◽

Air Flow Rate ◽

Cavity Configuration

Experimental results are given concerning the behavior of the flow around three-dimensional base-vented hydrofoils with wetted upper side. The influence of planform is given particular consideration so that the sections of the foils are simple wedges with rounded noses. Results concern cavity configuration, the relation between the air flow rate and cavity pressure, leading-edge cavitation, cavity length, pulsation frequency, and force coefficients.

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Generation Mechanism of Broadband Whoosh Noise in an Automotive Turbocharger Centrifugal Compressor

Journal of Turbomachinery ◽

10.1115/1.4051274 ◽

2021 ◽

pp. 1-35

Author(s):

Rick Dehner ◽

Pranav Sriganesh ◽

Ahmet Selamet ◽

Keith Miazgowicz

Keyword(s):

Centrifugal Compressor ◽

Combustion Engine ◽

Three Dimensional ◽

Leading Edge ◽

Broadband Noise ◽

Rotor Blades ◽

Generation Mechanism ◽

Primary Concern ◽

Frequency Range ◽

Modal Decomposition

Abstract The present study focuses on the acoustics of a turbocharger centrifugal compressor from a spark-ignition internal combustion engine. Whoosh noise is typically the primary concern for this type of compressor, which is loosely characterized by broadband sound elevation in the 4 to 13 kHz range. To identify the generation mechanism of broadband whoosh noise, the present study combines three approaches: three-dimensional (3D) computational fluid dynamics (CFD) predictions, experiments, and modal decomposition of 3D CFD results. After establishing the accuracy of predictions, flow structures and time-resolved pressures are closely examined in the vicinity of the main blade leading edge. This reveals the presence of rotating instabilities that may interact with the rotor blades to generate noise. An azimuthal modal decomposition is performed on the predicted pressure field to determine the number of cells and the frequency content of these rotating instabilities. The strength of the rotating instabilities and the frequency range in which noise is generated as a consequence of the rotor-rotating instability interaction, is found to correspond well with the qualitative trend of the whoosh noise that is measured several duct diameters upstream of the rotor blades. The variation of whoosh frequency range between low and high rotational speeds is interpreted through this analysis. It is also found that the whoosh noise primarily propagates along the duct as acoustic azimuthal modes. Hence, the inlet duct diameter, which governs the cut-off frequency for multi-dimensional acoustic modes, determines the lower frequency bound of the broadband noise.

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Experimental and Theoretical Investigation of the Supersonic Boundary Layer Stability on the Swept Wing

Siberian Journal of Physics ◽

10.54362/1818-7919-2008-3-3-34-38 ◽

2008 ◽

Vol 3 (3) ◽

pp. 34-38

Author(s):

Sergey A. Gaponov ◽

Yuri G. Yermolaev ◽

Aleksandr D. Kosinov ◽

Nikolay V. Semionov ◽

Boris V. Smorodsky

Keyword(s):

Boundary Layer ◽

Three Dimensional ◽

Leading Edge ◽

Supersonic Boundary Layer ◽

Mean Flow ◽

Swept Wing ◽

Wing Model ◽

Dimensional Boundary ◽

The Stability ◽

Good Agreement

Theoretical and an experimental research results of the disturbances development in a swept wing boundary layer are presented at Mach number М = 2. In experiments development of natural and small amplitude controllable disturbances downstream was studied. Experiments were carried out on a swept wing model with a lenticular profile at a zero attack angle. The swept angle of a leading edge was 40°. Wave parameters of moving disturbances were determined. In frames of the linear theory and an approach of the local self-similar mean flow the stability of a compressible three-dimensional boundary layer is studied. Good agreement of the theory with experimental results for transversal scales of unstable vertices of the secondary flow was obtained. However the calculated amplification rates differ from measured values considerably. This disagreement is explained by the nonlinear processes observed in experiment

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Vortex formation on surging aerofoils with application to reverse flow modelling

Journal of Fluid Mechanics ◽

10.1017/jfm.2018.800 ◽

2018 ◽

Vol 859 ◽

pp. 59-88 ◽

Cited By ~ 8

Author(s):

Philip B. Kirk ◽

Anya R. Jones

Keyword(s):

Surface Pressure ◽

Reverse Flow ◽

Vortex Formation ◽

Three Dimensional ◽

Tangential Velocity ◽

Leading Edge ◽

Field Measurements ◽

Reduced Frequency ◽

Advance Ratio ◽

Convection Speed

The leading-edge vortex (LEV) is a powerful unsteady flow structure that can result in significant unsteady loads on lifting blades and wings. Using force, surface pressure and flow field measurements, this work represents an experimental campaign to characterize LEV behaviour in sinusoidally surging flows with widely varying amplitudes and frequencies. Additional tests were conducted in reverse flow surge, with kinematics similar to the tangential velocity profile seen by a blade element in recent high-advance-ratio rotor experiments. General results demonstrate the variability of LEV convection properties with reduced frequency, which greatly affected the average lift-to-drag ratio in a cycle. Analysis of surface pressure measurements suggests that LEV convection speed is a function only of the local instantaneous flow velocity. In the rotor-comparison tests, LEVs formed in reverse flow surge were found to convect more quickly than the corresponding reverse flow LEVs that form on a high-advance-ratio rotor, demonstrating that rotary motion has a stabilizing effect on LEVs. The reverse flow surging LEVs were also found to be of comparable strength to those observed on the high-advance-ratio rotor, leading to the conclusion that a surging-wing simplification might provide a suitable basis for low-order models of much more complex three-dimensional flows.

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Calculation of Horseshoe Vortex Flow Without Numerical Mixing

Volume 1: Turbomachinery ◽

10.1115/84-gt-241 ◽

1984 ◽

Author(s):

Joan G. Moore ◽

John Moore

Keyword(s):

Three Dimensional ◽

Leading Edge ◽

Horseshoe Vortex ◽

Companion Paper ◽

New Method ◽

Uniform Grid ◽

Grid Spacing ◽

Three Dimensional Flow ◽

Numerical Mixing ◽

Well Posed

The usefulness of three-dimensional flow calculations has frequently been obscured by the numerical mixing present in the calculation methods. This paper describes a new method of forming the finite difference momentum equations. The new method results in well posed equations which introduce no numerical mixing. It may be used with orthogonal or non-orthogonal grids and with uniform or highly non-uniform grid spacing. The method is demonstrated by comparing it with upwind differencing on the calculation of a simple example. It is then used in an elliptic pressure-correction calculation procedure to calculate a leading edge horseshoe vortex about a Rankine half body. The results compare well with the experimental data presented in a companion paper.

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